Federal Register / Vol. 79, No. 90 / Friday, May 9, 2014 / Proposed Rules 26651 

3. Mail: Ms. Brenda Edwards, U.S. 

Department of Energy, Building 

Technologies Program, Mailstop EE–2J, 

1000 Independence Avenue SW., 

Washington, DC 20585–0121. If 

possible, please submit all items on a 

compact disc (CD), in which case it is 

not necessary to include printed copies. 

4. Hand Delivery/Courier: Ms. Brenda 

Edwards, U.S. Department of Energy, 

Building Technologies Program, 950 

L’Enfant Plaza SW., Suite 600, 

Washington, DC 20024. Telephone: 

(202) 586–2945. If possible, please 

submit all items on a CD, in which case 

it is not necessary to include printed 

copies. 

No telefacsimilies (faxes) will be 

accepted. 

Docket: The docket is available for 

review at www.regulations.gov, 

including Federal Register notices, 

public meeting and webinar attendee 

lists and transcripts, comments, and 

other supporting documents/materials. 

All documents in the docket are listed 

in the www.regulations.gov index. 

However, not all documents listed in 

the index may be publicly available, 

such as information that is exempt from 

public disclosure. 

The Secretary of Energy has approved 

publication of today’s document. 

Issued in Washington, DC, on May 5, 2014. 

Kathleen B. Hogan, 

Deputy Assistant Secretary for Energy 

Efficiency, Energy Efficiency and Renewable 

Energy. 

[FR Doc. 2014–10731 Filed 5–8–14; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0282; Directorate 

Identifier 2012–NM–168–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2006–0707, 

for certain A300 B4–600, B4–600R, and 

F4–600R series airplanes, and Model 

C4–605R variant F airplanes 

(collectively called A300–600 series 

airplanes). AD 2006–0707 requires 

modifying nine bolt holes in the vertical 

flange of the center spar sealing angles. 

Since we issued AD 2006–0707, we 

have received reports that fatigue and 

damage tolerance analyses show that the 

inspection threshold and interval must 

be reduced to allow timely detection of 

cracks. This proposed AD would 

continue to require modification of bolt 

holes in the vertical flange of the center 

spar sealing angles, and any applicable 

related investigative and corrective 

actions. This proposed AD would also 

require inspections for cracks, a 

modification by cold expansion of the 

center spar sealing angles, replacement 

of both sealing angles and cold 

expansion of the attachment holes if 

necessary, and post-repair repetitive 

inspections and corrective actions if 

necessary. We are proposing this AD to 

prevent crack formation in the sealing 

angles, which could rupture the sealing 

angle and lead to subsequent crack 

formation in the bottom skin of the 

wing, and result in reduced structural 

integrity of the center spar section of the 

wing. 

DATES: We must receive comments on 

this proposed AD by June 23, 2014. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS— 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may view this referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0282; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: Dan 

Rodina, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone (425) 227–2125; 

fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2014–0282; Directorate Identifier 

2012–NM–168–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On March 15, 2006, we issued AD 

2006–07–07, Amendment 39–14534 (71 

FR 16206, March 21, 2006). A correction 

of that AD was published in the Federal 

Register on April 21, 2006 (71 FR 

20530). That AD required actions 

intended to address an unsafe condition 

on certain Airbus Model A300–600 

series airplanes. 

Since we issued AD 2006–07–07, 

Amendment 39–14534 (71 FR 16206, 

March 21, 2006), we have received a 

report that additional actions are needed 

to address the unsafe condition. In 

addition, airplanes have been added to 

applicability. The applicability of AD 

2006–0707 excluded airplanes on which 

Airbus Modification 8609 was 

incorporated. We have determined that 

those airplanes must be inspected to 

address the unsafe condition. The 

European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD 2012– 

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26652 Federal Register / Vol. 79, No. 90 / Friday, May 9, 2014 / Proposed Rules 

0194, dated September 25, 2012 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

Fatigue testing applied to a test airframe 

confirmed the initiation of cracks on the 

sealing angles of the centre spar, adjacent to 

rib 8, which could lead to the rupture of the 

sealing angles and the subsequent crack 

initiation in the bottom skin of the wing. 

This condition, if not detected and 

corrected, could affect the structural integrity 

of the aeroplane. 

To address this unsafe condition, DGAC 

[French Civil Aviation Authority] France 

issued to require inspection of centre spar 

sealing angles adjacent to pylon rear 

attachment fittings of Left Hand (LH) and 

Right Hand (RH) wings. 

Early cracks reported on an in-service 

aeroplane prompted Airbus to conduct 

additional investigations. Based on the 

results, DGAC France issued AD 2003–290 

(later revised), which superseded DGAC 

France AD 91–253–128(B), to require 

modification of the affected aeroplanes as 

specified in Airbus Service Bulletin (SB) 

A300–57–6033 (Airbus Mod 8609), as well as 

post-modification repetitive inspections. 

Since DGAC France AD 2003–290(B)R1 

was issued, a fleet survey and updated 

Fatigue and Damage Tolerance analyses have 

been performed in order to substantiate the 

second A300–600 Extended Service Goal 

(ESG2) exercise. The results of these analyses 

have shown that the inspection threshold 

and interval must be reduced to allow timely 

detection of cracks on the sealing angles of 

the centre spar, adjacent to rib 8. 

For the reasons described above, this new 

[EASA] AD retains the requirements of DGAC 

France AD 2003–290(B) R1, which is 

superseded, and requires the 

accomplishment instructions at the new 

thresholds and intervals given by Revision 07 

of Airbus Service Bulletin (SB) A300–57– 

6027. 

The required actions also include 

repetitive high frequency eddy current 

(HFEC) inspections of the center spar 

sealing angles adjacent to the pylon re 

attachment fitting for cracks, modifying 

the airplane by cold expansion of the 

center spar sealing angles outboard of 

rib 8 if necessary, replacing both of the 

forward and aft sealing angles with new 

sealing angles and cold expanding the 

attachment holes if necessary, and doing 

post-repair repetitive inspections and 

corrective actions if necessary. You may 

examine the MCAI in the AD docket on 

the Internet at http://

www.regulations.gov by searching for 

and locating Docket No. FAA–2014– 

0282. 

Depending on the airplane 

configuration and airplane utilization, 

the compliance times are as follows: 

• For normal range operations, the 

initial compliance time for the new 

actions ranges between 9,000 flight 

cycles and 19,500 flight cycles, or 

within 18,600 flight hours and 40,300 

flight hours. The grace period for the 

action is within 1,700 flight cycles, or 

within 3,500 flight hours. 

• For short range operations, the 

initial compliance time for the new 

actions ranges between 10,600 flight 

cycles and 23,000 flight cycles, or 

within 15,900 flight hours and 34,500 

flight hours. The grace period for the 

action is within 2,000 flight cycles, or 

within 3,000 flight hours. 

• For normal range operations, the 

repetitive interval for the inspection is 

5,100 flight cycles or 10,500 flight 

hours. 

• For short-range operations, the 

repetitive interval for the inspection is 

6,000 flight cycles or 9,000 flight hours. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A300–57–6027, Revision 07, dated June 

6, 2011, and Service Bulletin A300–57– 

6033, Revision 02, dated September 19, 

2011. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

In many FAA transport ADs, when 

the service information specifies to 

contact the manufacturer for further 

instructions if certain discrepancies are 

found, we typically include in the AD 

a requirement to accomplish the action 

using a method approved by either the 

FAA or the State of Design Authority (or 

its delegated agent). 

We have recently been notified that 

certain laws in other countries do not 

allow such delegation of authority, but 

some countries do recognize design 

approval organizations. In addition, we 

have become aware that some U.S. 

operators have used repair instructions 

that were previously approved by a 

State of Design Authority or a Design 

Approval Holder (DAH) as a method of 

compliance with this provision in FAA 

ADs. Frequently, in these cases, the 

previously approved repair instructions 

come from the airplane structural repair 

manual or the DAH repair approval 

statements that were not specifically 

developed to address the unsafe 

condition corrected by the AD. Using 

repair instructions that were not 

specifically approved for a particular 

AD creates the potential for doing 

repairs that were not developed to 

address the unsafe condition identified 

by the MCAI AD, the FAA AD, or the 

applicable service information, which 

could result in the unsafe condition not 

being fully corrected. 

To prevent the use of repairs that 

were not specifically developed to 

correct the unsafe condition, this 

proposed AD would require that the 

repair approval specifically refer to the 

FAA AD. This change is intended to 

clarify the method of compliance and to 

provide operators with better visibility 

of repairs that are specifically developed 

and approved to correct the unsafe 

condition. In addition, we use the 

phrase ‘‘its delegated agent, or by the 

DAH with State of Design Authority 

design organization approval, as 

applicable’’ in this proposed AD to refer 

to an DAH authorized to approve 

required repairs for this proposed AD. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 21 products of U.S. registry. 

The actions that are required by AD 

2006–07–07, Amendment 39–14534 (71 

FR 16206, March 21, 2006), and retained 

in this proposed AD take about 25 workhours per product, at an average labor 

rate of $85 per work hour. Required 

parts cost about $1,249 per product. 

Based on these figures, the estimated 

cost of the currently required actions is 

$2,374 per product. 

We estimate that it would take about 

8 work-hours per product to comply 

with the new basic requirements of this 

proposed AD. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$14,280, or $680 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

about 42 work-hours and require parts 

costing $10,000, for a cost of $13,570 

per product. We have no way of 

determining the number of products 

that may need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

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Federal Register / Vol. 79, No. 90 / Friday, May 9, 2014 / Proposed Rules 26653 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2006–07–07, Amendment 39–14534 (71 

FR 16206, March 21, 2006); (corrected 

April 21, 2006 (71 FR 20530)), and 

adding the following new AD: 

Airbus: Docket No. FAA–2014–0282; 

Directorate Identifier 2012–NM–168–AD. 

(a) Comments Due Date 

We must receive comments by June 23, 

2014. 

(b) Affected ADs 

This AD supersedes AD 2006–07–07, 

Amendment 39–14534 (71 FR 16206, March 

21, 2006); (corrected April 21, 2006 (71 FR 

20530)). 

(c) Applicability 

This AD applies to Airbus Model A300 B4– 

601, B4–603, B4–620, and B4–622, B4–605R 

and B4–622R airplanes, Model A300 F4– 

605R and F4–622R airplanes, and Model 

A300 C4–605R Variant F airplanes, 

certificated in any category, except those on 

which Airbus Modification 8608 is 

incorporated. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 57, Wings. 

(e) Reason 

This AD was prompted by reports that 

fatigue and damage tolerance analyses shows 

that the inspection threshold and interval 

must be reduced to allow timely detection of 

cracks on the sealing angles of the center 

spar, adjacent to rib 8. We are issuing this AD 

to prevent crack formation in the sealing 

angles; such cracks could rupture the sealing 

angle and lead to subsequent crack formation 

in the bottom skin of the wing, and resultant 

reduced structural integrity of the center spar 

section of the wing. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Retained Modification 

This paragraph restates the requirements of 

paragraph (f) of AD 2006–07–07, Amendment 

39–14534 (71 FR 16206, March 21, 2006). For 

A300 B4–600, B4–600R, and F4–600R series 

airplanes, and Model C4–605R variant F 

airplanes (collectively called A300–600 

series airplanes); except those on which 

Airbus Modification 8608 or 8609 is 

incorporated: Within 500 flight cycles after 

April 17, 2006 (the effective date of AD 

2006–07–07, Amendment 39–14534, modify 

nine bolt holes in the vertical flange of the 

center spar sealing angles outboard of rib 8, 

adjacent to the pylon attachment fitting, and 

do any applicable related investigative and 

corrective actions before further flight; by 

doing all the actions in and in accordance 

with the Accomplishment Instructions of 

Airbus Service Bulletin A300–57–6033, 

Revision 01, dated December 18, 2003. If any 

crack is found during the related 

investigative action: Before further flight, 

repair in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6027, Revision 06, 

dated March 2, 2005. 

(h) Retained No Reporting Required 

This paragraph restates the reporting 

information of paragraph (g) of AD 2006–07– 

07, Amendment 39–14534 (71 FR 16206, 

March 21, 2006). Although Airbus Service 

Bulletin A300–57–6033, Revision 01, dated 

December 18, 2003, specifies to report crack 

findings to the manufacturer, this AD does 

not include that requirement. 

(i) New Requirement of this AD: Inspection 

and Modification 

For all airplanes, at the applicable time 

specified in paragraph (j) of this AD, 

accomplish the actions specified in 

paragraphs (i)(1) and (i)(2) of this AD 

concurrently. Repeat the inspection required 

by paragraph (i)(1) of this AD thereafter at 

intervals not to exceed the values as specified 

in the ‘‘Repeat Interval’’ column in Table 1 

or Table 2 of Airbus A300–57–6027, Revision 

07, dated June 6, 2011, as applicable to the 

airplane configuration and utilization; except 

as required by paragraph (m)(3) of this AD. 

(1) Do a high frequency eddy current 

(HFEC) inspection of the center spar sealing 

angles adjacent to the pylon re-attachment 

fitting for cracks, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6027, Revision 07, 

dated June 6, 2011. 

(2) Unless already done: Modify the 

airplane by cold expansion of the center spar 

sealing angles outboard of Rib 8, adjacent to 

the pylon rear attachment fitting, including 

doing the eddy current inspections for cracks 

of the bolt holes, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A300–57–6033, Revision 02, 

dated September 19, 2011. 

(j) Initial Compliance Times 

At the later of the times specified in 

paragraph (j)(1) and (j)(2) of this AD, except 

as required by paragraph (m) of this AD, do 

the actions required by paragraph (i) of this 

AD. 

(1) At the applicable compliance time 

specified in Table 1 and Table 2 in the 

‘‘Threshold Inspection,’’ column in 

paragraph 1.E., ‘‘Compliance,’’ of Airbus 

Service Bulletin A300–57–6027, Revision 07, 

dated June 6, 2011. 

(2) At the applicable compliance time 

specified in Table 1 and Table 2 in the 

‘‘Grace Period,’’ column in paragraph 1.E., 

‘‘Compliance,’’ of Airbus Service Bulletin 

A300–57–6027, Revision 07, dated June 6, 

2011. 

(k) New Requirement of This AD: Corrective 

Action 

If, during any inspection required by 

paragraph (i)(1) or (i)(2) of this AD, any crack 

is found: Before further flight, repair the 

crack by replacing both of the forward and 

aft sealing angles with new sealing angles 

and cold expansion of the attachment holes, 

in accordance with the Accomplishment 

Instructions of Airbus Service Bulletin A300– 

57–6027, Revision 07, dated June 6, 2011. 

The corrective actions, as required by this 

paragraph, does not constitute as a 

terminating action for the repetitive 

inspections in paragraph (i)(1) of this AD. 

(l) New Requirement of This AD: Post 

Modification Actions 

After modification of the airplane, as 

specified in Airbus Service Bulletin A300– 

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26654 Federal Register / Vol. 79, No. 90 / Friday, May 9, 2014 / Proposed Rules 

57–6027, Revision 07, dated June 6, 2011: 

Within 3 months after the effective date of 

this AD, or before further flight after doing 

the modification, whichever occurs later, 

contact the FAA, ANM–116, Transport 

Airplane Directorate, or EASA (or its 

delegated agent, or the Design Approval 

Holder (DAH) with EASA design 

organization approval, as applicable) for 

repetitive post-repair inspections and 

corrective actions, and do those actions. 

(m) Exceptions to the Service Bulletin 

(1) Where Note 01 and Note 02 of 

paragraph 1.E., ‘‘Compliance,’’ of Airbus 

Service Bulletin A300–57–6027, Revision 07, 

dated June 6, 2011, specifies to contact 

Airbus for inspection requirements, this AD 

requires, at the applicable compliance time 

specified in Table 1 and Table 2 in the 

‘‘Grace Period,’’ column in paragraph 1.E., 

‘‘Compliance,’’ of Airbus Service Bulletin 

A300–57–6027, Revision 07, dated June 6, 

2011, to repair using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

European Aviation Safety Agency (EASA) (or 

its delegated agent, or the Design Approval 

Holder (DAH) with EASA design 

organization approval, as applicable). For a 

repair method to be approved, the repair 

approval must specifically refer to this AD. 

(2) Where the Airbus Service Bulletin 

A300–57–6027, Revision 07, dated June 6, 

2011 specifies a compliance time in Table 1 

and Table 2 in the ‘‘Grace Period,’’ column 

in paragraph 1.E., ‘‘Compliance,’’ this AD 

requires compliance within the specified 

compliance time after the effective date of 

this AD. 

(3) Where Table 1 and Table 2 in paragraph 

1.E., ‘‘Compliance,’’ of Airbus Service 

Bulletin A300–57–6027, Revision 07, dated 

June 6, 2011, specifies a choice between 

flight cycle or flight hours, this AD requires 

a compliance time within the specified flight 

cycles or flight hours, whichever occurs first. 

(4) Where Table 1 and Table 2 in paragraph 

1.E., ‘‘Compliance,’’ of Airbus Service 

Bulletin A300–57–6027, Revision 07, dated 

June 6, 2011, specifies pre-modification 8609, 

this AD requires compliance within the 

compliance time specified in the ‘‘Threshold 

Inspection’’ column. Those compliance times 

are flight cycles or flight hours since new. 

(5) Where Table 1 and Table 2 in paragraph 

1.E., ‘‘Compliance,’’ of Airbus Service 

Bulletin A300–57–6027, Revision 07, dated 

June 6, 2011, specifies any post modification 

or repair, this AD requires compliance within 

the compliance time specified in the 

‘‘Threshold Inspection’’ column. Those 

compliance times are flight cycles or flight 

hours since accomplishing the modification 

or repair. 

(n) Credit for Previous Actions 

This paragraph provides credit for actions 

required by paragraph (i)(1) of this AD, if 

those actions were performed before the 

effective date of this AD using the service 

information in paragraph (n)(i) through 

(n)(iii) of this AD. 

(i) Airbus Service Bulletin A300–57–6027, 

Revision 04, dated August 4, 1999. 

(ii) Airbus Service Bulletin A300–57–6027, 

Revision 05, dated November 21, 2002. 

(iii) Airbus Service Bulletin A300–57– 

6027, Revision 06, dated March 2, 2005. 

(o) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Dan Rodina, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone (425) 227–2125; fax (425) 227– 

1149. Information may be emailed to: 9- 

ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. AMOCs approved previously for AD 

98–18–02, Amendment 39–10718 (63 FR 

45689, August 27, 1998), are approved as 

AMOCs for the corresponding provisions in 

paragraph (g) of this AD. 

(3) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(p) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA AD 

2012–0194, dated September 25, 2012, for 

related information. This MCAI may be 

found in the AD docket on the Internet at 

http://www.regulations.gov by searching for 

and locating Docket No. FAA–2014–0282. 

(2) For service information identified in 

this AD, contact Airbus SAS—EAW 

(Airworthiness Office), 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airwortheas@airbus.com; Internet http:// 

www.airbus.com. You may view this service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

WA. For information on the availability of 

this material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on May 2, 

2014. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2014–10682 Filed 5–8–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF COMMERCE 

National Oceanic and Atmospheric 

Administration 

15 CFR Part 922 

[Docket No. 130403324–4310–02] 

RIN 0648–BC94 

Boundary Expansion of Thunder Bay 

National Marine Sanctuary 

AGENCY: Office of National Marine 

Sanctuaries (ONMS), National Ocean 

Service (NOS), National Oceanic and 

Atmospheric Administration (NOAA), 

Department of Commerce (DOC). 

ACTION: Amendment to proposed rule; 

request for public comments. 

SUMMARY: The National Oceanic and 

Atmospheric Administration (NOAA) 

hereby amends a proposed rule 

published on June 14, 2013. The June 

14, 2013 proposed rule sought to 

expand the boundary of Thunder Bay 

National Marine Sanctuary (TBNMS or 

sanctuary) and revise the corresponding 

sanctuary terms of designation. This 

rule focuses specifically on modifying 

the proposed boundary of the sanctuary, 

addressing questions and concerns on 

ballasting operations within the 

proposed expansion area, and clarifying 

the correlation between TBNMS 

regulations and Indian tribal fishing 

activities. NOAA is soliciting public 

comment only on the amendments in 

this proposed rule. Previously 

submitted public comments need not be 

resubmitted. 

DATES: Comments will be considered if 

received by June 9, 2014. 

ADDRESSES: You may submit comments 

on this document, identified by NOAA– 

NOS–2012–0077, by any of the 

following methods: 

• Electronic Submissions: Submit all 

electronic public comments via the 

Federal e-Rulemaking Portal. Go to 

www.regulations.gov/

#!docketDetail;D=NOAA-NOS-2012- 

0077, click the ‘‘Comment Now!’’ icon, 

complete the required fields and enter 

or attach your comments. 

• Mail: Submit written comments to 

Thunder Bay National Marine 

Sanctuary, 500 W. Fletcher, Alpena, 

Michigan 49707, Attn: Jeff Gray, 

Superintendent. 

Instructions: Comments sent by any 

other method, to any other address or 

individual, or received after the end of 

the comment period may not be 

considered by NOAA. All comments 

received are a part of the public record 

and will be posted for public viewing on 

www.regulations.gov without change. 

mstockstill on DSK4VPTVN1PROD with PROPOSALS